CN101282879B - Parked aircraft power cable protection system and method - Google Patents
Parked aircraft power cable protection system and method Download PDFInfo
- Publication number
- CN101282879B CN101282879B CN200680037500.6A CN200680037500A CN101282879B CN 101282879 B CN101282879 B CN 101282879B CN 200680037500 A CN200680037500 A CN 200680037500A CN 101282879 B CN101282879 B CN 101282879B
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- Prior art keywords
- ring
- semi
- cable
- cable assembly
- inner ring
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- 238000005728 strengthening Methods 0.000 claims description 6
- 239000004677 Nylon Substances 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 claims description 3
- 239000011521 glass Substances 0.000 claims description 3
- 229920001778 nylon Polymers 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims 7
- 238000010168 coupling process Methods 0.000 claims 7
- 238000005859 coupling reaction Methods 0.000 claims 7
- 239000000463 material Substances 0.000 claims 4
- 239000002991 molded plastic Substances 0.000 claims 4
- 239000011248 coating agent Substances 0.000 claims 2
- 238000000576 coating method Methods 0.000 claims 2
- 230000002787 reinforcement Effects 0.000 claims 2
- 230000001681 protective effect Effects 0.000 abstract 2
- 238000009413 insulation Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
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- 238000009434 installation Methods 0.000 description 2
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- 230000004048 modification Effects 0.000 description 2
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- 230000015572 biosynthetic process Effects 0.000 description 1
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Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/36—Other airport installations
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laying Of Electric Cables Or Lines Outside (AREA)
- Installation Of Indoor Wiring (AREA)
Abstract
A power delivery system for parked aircraft includes protective rings (20) on the power cords (18). These protective rings (20) protect the power cord jackets from wear and facilitate movement of the power cords across the ground. The rings (20) may be configured for securement to the cable (18) so as to compress the insulative jacket of the cable somewhat, thereby firmly maintaining the rings in place on the cable. The rings may be formed of two identical elements (22, 24) that are joined to envelope the cable. The rings may accommodate both round insulated cable, as well as bundled cable.
Description
Technical field
Generally speaking, the present invention relates to a kind of aircraft power delivery systems.More particularly, the present invention relates to a kind of protection cable and cable assembly, and the technology on road surface is more easily crossed in the place that described cable may be at a stop at terminal or other aircraft.
Background technology
On most of aircrafts, have a plurality of for the electrical power transmission system during different operating.Namely, in-flight or the electric system of the aircraft slided on runway by auxiliary power unit (APU), driven, this device generally includes the driving engine be connected with electrical generator or alternating current generator, as in automobile.On the other hand, the aircraft be at a stop is driven by external power supply usually.These external power supplys can be mobile generator system or the electric installation that is built in terminal, passenger bridges or hangarage.
In order from external power supply, to supply electric energy to the aircraft be at a stop, aircraft must complete and electric installation connection.The equipment that must be switched on the ability supply of electrical energy with majority is the same, and aircraft is connected to power supply unit by power cord or cable.Cable or cable assembly usually need based on voltage and current and select.For instance, the established industry standard about the particular aircraft power cable is to provide specified 260 amperes and the power supply of 400 hertz.
As expected, more much bigger than standard household electric power cable for the electric wireline of connecting aircraft.For example, the external diameter of these cables is approximately 1 to 2 inch.Can select, these electric wireline can be comprised of a plurality of little cable banded together in fact.In addition, because described aircraft can not always approach the externally fed unit, so some cable must be quite long.With regard to commercial aircraft, other position that these cables must be at a stop from landing gate or aircraft usually starts to extend, and then crosses hardstand and arrives the terminal building that power supply unit is positioned at or arrive portable power supply.
Be understandable that, due to its length and thickness larger, so these cables are very heavy.For example, the cable of 260 amperes, 400 hertz types as above, it is 60 feet long, its weight can be over 130 pounds.The staff must move that these cables are crossed the road surface, hardstand and the runway road surface extends to aircraft by cable from mains connection set.And drag long and heavy cable, to cross road surface be very difficult, also can inevitably cause the cable wearing and tearing and cable insulation jacket is degenerated.
A kind of solution that makes cable more easily cross road surface is to coat smooth insulating sheath at cable surface.This smooth sheath slides more easily cable and crosses hardstand and runway.Yet this solution can not solve the problem of cable wearing and tearing, and the degeneration in time of smooth insulating sheath even can make these cables be difficult to operation.
So, provide a kind of and make the aricraft electrical power cable very easily cross road surface and also can prevent that the system of the insulating sheath wearing and tearing of cable from being very useful simultaneously.
Summary of the invention
According to a particular embodiment of the invention, the cable assembly that protection ring is supplied electric power with the aircraft for being at a stop is connected.These rings are designed so that more easily negotiate terrain of cable assembly.Similarly, these encircle compressed being fixed on cable assembly, make each ring probably remain on its initial position with respect to cable assembly.Each ring can be comprised of two identical semi-rings, thus time and the cost that can reduce assembling and produce.Semi-ring is fixed together by lockable mechanism, next will be described its a plurality of embodiment.
The other embodiment according to the present invention, protection ring is configured to be connected with the cable assembly of tying up.The cable assembly of this pattern can be replaced by single cable assembly.
The accompanying drawing explanation
After having read ensuing description with reference to relevant drawings, these or further feature, characteristics and advantage of the present invention will be better understood, and in described accompanying drawing, identical Reference numeral means similar parts, wherein:
Accompanying drawing 1 is according to embodiments of the invention, schematic diagram aircraft is connected with power supply unit by the power cable assembly with protection ring;
Accompanying drawing 2 is transparents view of the power cable assembly with ring shown in accompanying drawing 1;
Accompanying drawing 3 is transparents view that amplify the part of power cable assembly in accompanying drawing 2;
Accompanying drawing 4 is transparents view of parts in accompanying drawing 3;
Accompanying drawing 5 is the cutaway views of the ring 5-5 along the line in accompanying drawing 3;
Accompanying drawing 6 is the transparents view according to parts of the power cable assembly of the embodiment of the present invention and protection ring;
Accompanying drawing 7 is the transparents view according to the parts of alternative protection ring of the power cable assembly of the embodiment of the present invention and design;
Accompanying drawing 8 is the transparents view according to the parts of another alternative protection ring of the power cable assembly of the embodiment of the present invention and design;
Accompanying drawing 9 is the transparents view according to the parts of further alternative protection ring of the power cable assembly of the embodiment of the present invention and design;
Accompanying drawing 10 is the transparents view for parts of further alternative protection ring of many cable assemblies;
Accompanying drawing 11 is the transparents view of parts with many cables of tying up power cable assembly of the protection ring pattern shown in accompanying drawing 10;
Accompanying drawing 12 is transparents view of parts of another the alternative protection ring similar to accompanying drawing 10, but its many cable assemblies for being formed by a pair of cable;
Accompanying drawing 13 is the transparents view of parts that are mounted many power cables of tying up assembly of protection ring shown in Figure 12.
The specific embodiment
Specifically with reference to accompanying drawing 1, its show the aircraft that is at a stop by the electrical power transmission system shown in Reference numeral 10.As shown in FIG., can be business, army or private aircraft 12, it is parked on the ground 14 as terminal or other base.Ground 14 can be hardstand, runway or hangar floor usually, but can be also other any ground that aircraft is parked.Aircraft 12 is connected on power supply unit 16 by cable assembly 18.As those skilled in the desired, power supply unit 16 can be wheeled apparatus (as engine-driven electrical generator unit), or can be the device (as the power supply shown with frame table in figure) that is fixed on appropriate location.For above-mentioned any situation, the operation transferring electric power that cable assembly 18 is the aircraft different system, thus can reduce the needs of the airborne energy source that utilizes aircraft itself.
When aircraft 12 motion, for example, when it slides to terminal or skids off from terminal, cable assembly 18 must move apart aircraft 12.When aircraft 12 is parked, cable assembly 18 is shifted near and is connected with aircraft 12, thereby completes the electrical connection between power supply unit 16 and aircraft 12.Aircraft 12 start mobile before, cable assembly 18 disconnects and moves apart aircraft with aircraft 12, makes it not on the path of aircraft 12 or makes it can be used to power supply unit 16 is connected on another aircraft.As mentioned above, the cable assembly weight with 260 amperes, 400 hertz of standards of 1.65 inches of external diameters surpasses 130 pounds, and cable assembly may be longer and/or thicker than this standard.
As further describing of accompanying drawing 2 and 3, one section of protection ring 20 and cable assembly 18 is connected.In the illustrated embodiment, each protection ring 20 is comprised of the first semi-ring 22 and the second semi-ring 24.The outer ring 26 of each ring is configured to lean against on areal of support, as described on ground 14, and it can be along ground during service personnel removal cable assembly 14 slides.As ensuing, describe in further detail, the inner ring 28 of each ring is configured to lean against on the outer insulation jacket 30 of cable assembly 18 and compresses outer insulation jacket.Semi-ring 22,24 is fixed together at joint 32.Have groove 34 on the outer ring 26 of each semi-ring 22,24, it is for leading to locking element 44, with reference to the detailed description of attached Figure 4 and 5.
In the embodiment of this expection, that are identical for semi-ring 22 and semi-ring 24, and are designed so that relative semi-ring 22 deflections of semi-ring 24 and mutual aspectant cooperation.Engage semi-ring, so just formed a complete protection ring 20.Attached Figure 4 and 5 show other possible arrangement form of half engagement of loops.
According to the embodiment of this expection, with reference to accompanying drawing 4, it shows the semi-ring 22 of protection ring 20.As mentioned above.Semi-ring 24 is identical with semi-ring 22.Each semi-ring can be formed by any suitable job operation, as utilizes plastics, and for example glass is strengthened the injection mo(u)lding of nylon.Because semi-ring 22,24 is identical, only need an injection mould for producing each ring, therefore can reduce the assembly of devices relevant to the manufacture of ring originally.In addition, due to the equal complete ring of formation capable of being combined of any two semi-rings, so can make productive costs minimize.That is to say, because the parts of any two manufacturings all are enough to form a ring, therefore without two different component combinations that guarantee ring together.
Attached Figure 4 and 5 illustrate the exemplary enforcement body that semi-ring 22,24 is linked together.In this embodiment, relative semi-ring 22 reversions of semi-ring 24.Locking element 44 comprises cam face 46, is configured to crossing locking surface 48 deflection locking element 44 flexibly while inserting engagement opening 50.Locking surface 48 be arranged to for prevent locking element 44 from the engagement opening 50 deviate from.Engagement opening 50 comprises and is configured to together with cam face 46 the flexibly outward flange of deflection locking element 44, but also comprises and be arranged to the stop surfaces 56 that prevents that locking element 44 from deviating from from engagement opening 50.Groove 34 is arranged for and leads to locking element 44.
The assembling of semi-ring 22,24 is as described below.When reversion, groove 54 aligns with projection 52.These projections 52 and groove 54 are configured to help semi-ring 22,24 appropriate location, and provide aiding support at 32 pairs of protection rings 20 of joint.When semi-ring 22 and the semi-ring 24 of reversion are adjacent, cam face 46 touches with the side edge of engagement opening 50.When semi-ring 22,24 moves together, the pressure acted on cam face 46 by engagement opening 50 makes locking element 44 deflections.Once cam face 46 integrated movings are by the stop surfaces 56 in engagement opening 50, locking element 44 roughly turns back to its initial position.Then locking surface 48 with stop surfaces 56, contact static, thereby can prevent that locking element 44 from deviating from from mesh opening 50.
With reference to accompanying drawing 6-9, the alternate embodiment of semi-ring 22 illustrates together with power cable assembly 18.These alternate embodiments of semi-ring 22 have the architectural feature roughly the same with above-mentioned semi-ring.Wherein show a plurality of possible lockable mechanisms.Accompanying drawing 6 is the schematic diagrams with semi-ring 22 of elastic deflection locking element 44, can be with reference to the description of above-mentioned attached Figure 4 and 5.
Accompanying drawing 7 illustrates the alternative embodiment of the present invention, and wherein, semi-ring 22,24 is connected with nut 62 by bolt 60.In this embodiment, semi-ring 22,24 by as above protruding 52 and groove 54 locate.The hole 58 at semi-ring 22 two ends is configured for receiving bolt 60.Bolt 60 is installed fixing by nut 62.
Accompanying drawing 8 illustrates further alternative embodiment of semi-ring 22.In this embodiment, semi-ring 22 comprises the central channel 64 for receiving hoop 66.Semi-ring 22,24 links together by hoop 66.Those skilled in the art are apprehensible, and hoop 66 can comprise that helical clamping, hoop clamp or the fastener of other general toroidal.
Accompanying drawing 9 illustrates another alternative embodiment of semi-ring 22, and in this embodiment, semi-ring 22 comprises for receiving the locking projection 68 of needle roller 70.When needle roller 70 is inserted into locking projection 68, semi-ring 22,24 is fixed together.
Specifically, with reference to accompanying drawing 10 and 11, it shows the further embodiment of the present invention.The further feature of this embodiment and lockable mechanism are similar to the embodiment's shown in attached Figure 4 and 5.In this embodiment, protection ring 20 is configured to be connected on the cable assembly 76 of tying up.As those skilled in the desired, for providing cable assembly 76 that the standard of electric power is tied up to surround less cable by 4 independent insulated cable parts, the aircraft 12 be at a stop forms.As shown in Figure 10, inner ring 28 can be roughly knuckle-tooth shape or leaf, and its shape with the cable assembly 76 of tying up is consistent.Inner ring 28 roughly crenate shape comprises a complete recess 74 and two part recesses 72, and this complete recess is for holding the parts of the whole cable assembly of tying up 76, and each part recess is for half of the parts that hold the cable assembly 76 of tying up.With reference to the description of above-mentioned attached Figure 4 and 5, the flange 40 of inner ring 28 can be arranged for the insulating sheath of the parts that compress the cable assembly 76 of tying up, thereby protection ring 20 can not be free to slide along the cable assembly 76 of tying up.In addition, according to this embodiment, above-mentioned arbitrary lockable mechanism can be used to connect semi-ring 22,24.
Next, with reference to accompanying drawing 12 and 13, it shows the different embodiment of protection ring 20.Semi-ring shown in accompanying drawing 12 is identical with shown in accompanying drawing 10 basically.Yet the ring in accompanying drawing 12 and 13 is for holding the paired cable bundle.Therefore, two part recesses 72 form the inner ring 28 of each ring, thereby make its contact and compress a little the insulating sheath that is arranged in two cables.The form of the ring shown in accompanying drawing 12 and 13 is specially adapted to provide galvanic cable assembly.It should be noted that, the protection ring of the many cables shown in accompanying drawing 10,11,12 and 13 and paired cable assembly, it has also comprised cable harness or the structure of assembly or the structure that multi-form cable is banded together of other applicable varying number.
Only illustrate and described some feature of the present invention herein, those skilled in the art can make various deformation and modification to it.Therefore, be understandable that, the claim that intention covers modifications and variations all falls in connotation scope of the present invention.
Claims (21)
1. an aircraft floor electrical power transmission system comprises:
The power cable assembly, its be configured to be connected to power supply and the aircraft that is at a stop between; With
A plurality of rings, each ring has inner ring and outer ring, the inner ring of each ring is fixed on the insulating sheath of cable assembly compressively, the outer ring of each ring is the supporting cable assembly at least in part, for power cable is promoted from area supported, and the slip that makes cable assembly cross area supported is more prone to;
Each ring is comprised of two identical semi-rings, and described inner ring comprises the strengthening rib be configured at least at each semi-loop of axial direction upper support of ring.
2. the system as claimed in claim 1, is characterized in that, the cross-sectional plane of cable assembly is circular, and the inner ring of each ring is the circle consistent with the shape of cable assembly insulating sheath, and less than the nominal dimension of insulating sheath outside face.
3. the system as claimed in claim 1, it is characterized in that, cable assembly comprises a plurality of independent insulated cables, and these cables band together and form knuckle-tooth shape or leaf outer shape, and wherein, the inner ring of each ring is knuckle-tooth shape or the leaf shape consistent with the outer shape of cable assembly.
4. the system as claimed in claim 1, is characterized in that, each ring is formed by molded plastic material.
5. system as claimed in claim 4, is characterized in that, molded plastic material comprises glass reinforcement nylon.
6. the system as claimed in claim 1, is characterized in that, the inner ring of each ring has the flange engaged with the insulating sheath of described cable assembly.
7. a power cable assembly fender guard comprises:
The aricraft electrical power cable; With
Ring with inner ring and outer ring, inner ring is configured to be fixed to compressively on the insulating sheath of described Aircraft Cables, outer ring is configured to support at least in part described Aircraft Cables for described cable is promoted from area supported, and described cable is more prone in the slip of area supported;
Each ring is comprised of two identical semi-rings, and described inner ring comprises the strengthening rib be configured at least at each semi-loop of axial direction upper support of ring.
8. device as claimed in claim 7, is characterized in that, inner ring is circular.
9. device as claimed in claim 7, is characterized in that, inner ring is the knuckle-tooth shape consistent with the knuckle-tooth shape of the cable assembly of tying up or leaf outer shape or leaf.
10. device as claimed in claim 7, is characterized in that, ring is formed by molded plastic material.
11. device as claimed in claim 10, is characterized in that, molded plastic material comprises glass reinforcement nylon.
12. device as claimed in claim 7, is characterized in that, inner ring comprises the flange engaged with the insulating sheath of cable assembly.
13. device as claimed in claim 7, is characterized in that, each semi-ring comprises locking element and corresponding coupling opening.
14. device as claimed in claim 7, is characterized in that, each semi-ring comprises one or more positioning convex and one or more corresponding positioning groove.
15. device as claimed in claim 7, is characterized in that, a semi-ring is configured to another semi-ring deflection relatively, to form complete ring.
16. a power cable assembly fender guard comprises:
Power cable; With
A plurality of rings of fixing along described cable, each ring has inner ring and outer ring, inner ring is configured to be fixed to compressively on the insulating sheath of described cable, outer ring is configured to support at least in part described cable for cable is promoted from area supported, and described cable is more prone in the slip of area supported;
Each ring comprises two identical semi-rings, and one of them semi-ring is configured to respect to another semi-ring deflection, and to form complete ring, described inner ring comprises the strengthening rib be configured at least at each semi-loop of axial direction upper support of ring.
17. device as claimed in claim 16, is characterized in that, each semi-ring comprises the flange engaged with the insulating sheath of cable assembly.
18. device as claimed in claim 16, is characterized in that, each semi-ring comprises at least one positioning convex and at least one corresponding positioning groove.
19. device as claimed in claim 16, is characterized in that, each semi-ring comprises locking element and corresponding coupling opening.
20. device as claimed in claim 19, it is characterized in that, locking element comprises cam face and locking surface, and wherein coupling opening comprises coating surface, cam face elastic deflection locking element when locking element is inserted into coupling opening, and locking wherein surface and coating surface are in contact with one another to prevent that locking element from deviating from from coupling opening.
21. device as claimed in claim 20, is characterized in that, coupling opening comprises the groove that holds cam face, for the deflection locking element, to deviate from from coupling opening.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/227,330 US7572981B2 (en) | 2005-09-14 | 2005-09-14 | Parked aircraft power cable protection system and method |
| US11/227,330 | 2005-09-14 | ||
| PCT/US2006/030175 WO2007040790A1 (en) | 2005-09-14 | 2006-08-03 | Parked aircraft power cable protection system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101282879A CN101282879A (en) | 2008-10-08 |
| CN101282879B true CN101282879B (en) | 2013-12-25 |
Family
ID=37735032
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200680037500.6A Expired - Fee Related CN101282879B (en) | 2005-09-14 | 2006-08-03 | Parked aircraft power cable protection system and method |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US7572981B2 (en) |
| CN (1) | CN101282879B (en) |
| DE (1) | DE112006002426T5 (en) |
| WO (1) | WO2007040790A1 (en) |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100038506A1 (en) * | 2008-08-14 | 2010-02-18 | King Jr Lloyd Herbert | Self-Connectors |
| FR2943256A1 (en) * | 2009-03-20 | 2010-09-24 | Fresenius Medical Care De Gmbh | ADAPTER FOR CONNECTING A CONTAINER CONNECTOR TO A CONNECTION SOCKET OF A DIALYSIS MACHINE |
| AU2010250113B2 (en) * | 2009-05-22 | 2015-03-26 | Tyco Fire & Security Gmbh | Fitting for forming a joint for coupling fire fighting hose |
| US8459296B2 (en) | 2010-08-20 | 2013-06-11 | Illinois Tool Works | Aircraft hose retrieval system |
| CN102013647B (en) * | 2010-10-28 | 2013-08-07 | 北京航空航天大学 | Rapid detachable cable fixing piece |
| CN103066498B (en) * | 2012-12-28 | 2015-05-20 | 国家电网公司 | High voltage equipment cable protection ring |
| US9617005B1 (en) * | 2013-07-31 | 2017-04-11 | Peter Schiff | System and method for replacing an engine powered air conditioning unit with an electric air conditioning unit in an aircraft |
| CN104676120A (en) * | 2015-03-11 | 2015-06-03 | 国家电网公司 | Power cable spacing clamp |
| US10008840B2 (en) | 2015-07-20 | 2018-06-26 | Magnetic Lifting Technologies US, LLC | Flexible clad protection system |
| CN106506062B (en) * | 2016-11-29 | 2020-01-21 | 中山大学 | Distributed rapid communication system and communication method for cluster unmanned aerial vehicle |
| CN108831604B (en) * | 2018-07-16 | 2023-09-29 | 中国人民解放军海军航空大学青岛校区 | Electromagnetic shielding cable for aircraft |
| US11384891B1 (en) * | 2021-02-27 | 2022-07-12 | John Stone | Hose protector device |
| CN114576438B (en) * | 2022-03-14 | 2023-03-14 | 南京新核复合材料有限公司 | Large-diameter glass fiber reinforced plastic pipeline and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3913187A (en) * | 1973-10-18 | 1975-10-21 | Nifco Inc | Squeeze-action clamp |
| GB1538453A (en) * | 1977-07-05 | 1979-01-17 | Armshire Sherville Plastics Lt | Supports for pipework |
| US4637097A (en) * | 1985-10-21 | 1987-01-20 | Chrysler Motors Corporation | Cable bundler clip |
| US5115586A (en) * | 1988-02-17 | 1992-05-26 | Development Technology Limited | Cable markers |
| US6633000B2 (en) * | 2001-02-23 | 2003-10-14 | Hon Hai Precision Ind. Co., Ltd. | Noise filter with an improved insulating case |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1327659A (en) | 1971-09-27 | 1973-08-22 | Weatherhead Co | Abrasion resistant flexible hose |
| FR2200840A5 (en) | 1972-09-25 | 1974-04-19 | Frangeco | |
| US4843356A (en) * | 1986-08-25 | 1989-06-27 | Stanford University | Electrical cable having improved signal transmission characteristics |
| US5003278A (en) * | 1990-03-01 | 1991-03-26 | Ferrishield, Inc. | Ferrite suppressor case with retaining fingers |
| DK168240B1 (en) * | 1992-02-14 | 1994-02-28 | Aqua Flow Aps | Hose protector and hose provided with such hose protector |
| DE4236560A1 (en) * | 1992-10-29 | 1994-05-05 | Kabelmetal Electro Gmbh | Electric cable - has sleeve formed by copper inner and steel outer layers, with insulation between |
| AUPO711097A0 (en) * | 1997-06-02 | 1997-06-26 | National Valve & Engineering Company Pty. Limited | Hose protector system |
| US7484689B2 (en) * | 2002-07-19 | 2009-02-03 | Illinois Tool Works Inc. | Aviation ground power unit connection system and method incorporating same |
-
2005
- 2005-09-14 US US11/227,330 patent/US7572981B2/en active Active
-
2006
- 2006-08-03 DE DE112006002426T patent/DE112006002426T5/en not_active Withdrawn
- 2006-08-03 WO PCT/US2006/030175 patent/WO2007040790A1/en active Application Filing
- 2006-08-03 CN CN200680037500.6A patent/CN101282879B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3913187A (en) * | 1973-10-18 | 1975-10-21 | Nifco Inc | Squeeze-action clamp |
| GB1538453A (en) * | 1977-07-05 | 1979-01-17 | Armshire Sherville Plastics Lt | Supports for pipework |
| US4637097A (en) * | 1985-10-21 | 1987-01-20 | Chrysler Motors Corporation | Cable bundler clip |
| US5115586A (en) * | 1988-02-17 | 1992-05-26 | Development Technology Limited | Cable markers |
| US6633000B2 (en) * | 2001-02-23 | 2003-10-14 | Hon Hai Precision Ind. Co., Ltd. | Noise filter with an improved insulating case |
Also Published As
| Publication number | Publication date |
|---|---|
| DE112006002426T5 (en) | 2008-07-03 |
| CN101282879A (en) | 2008-10-08 |
| US7572981B2 (en) | 2009-08-11 |
| WO2007040790A1 (en) | 2007-04-12 |
| US20070056761A1 (en) | 2007-03-15 |
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